Abstract: A method for automating a landing maneuver for an aircraft, comprising the steps of generating an approach profile comprising an initial approach fix (IAF), a flight path, a landing decision point, a balked landing route, a pre-landing point, and a landing point, engaging an automated approach system to access the approach profile, receiving periodic position data of the aircraft, comparing the position data to the approach profile to compute a plurality of deviations each time the position data is received, outputting the plurality of deviations to a display, converting the plurality of deviations into a plurality of control commands, and maneuvering the aircraft in response to the control commands along the flight path.

Abstract: A system, method, and computer program product for alerting an aircraft flight crew of an inconsistency during an instrument landing system (ILS) approach to a selected runway. The system includes a component configured to receive glideslope and localizer signals, and a component configured to determine aircraft approach angle to runway end. Also, a component configured to alert the aircraft flight crew of an approach inconsistency, if the determined aircraft approach angle to runway end is less than a threshold angular value and one or more parameters based on aircraft position and the received glideslope and localizer signals are met. The component configured to determine aircraft approach angle to runway end determines the aircraft approach angle to runway end based on aircraft geometric altitude, a vertical figure of merit, a horizontal figure of merit, runway elevation, and aircraft distance to runway threshold.

Abstract: An approach suppressed TAWS system and method for suppressing nuisance alarms based upon a determination that an aircraft is properly aligned for landing based upon location within a safe zone defined by a glideslope component and a localizer component.

Abstract: A system and method for displaying target vehicle position that combines the data available from a plurality of surveillance sensors. Data from the plurality of sensors is fused to calculate a composite target position and a projected track for each vehicle within the range of the sensors. The composite data is also used to calculate a boundary of certainty for both the position and the projected track. The position, projected track and the boundaries of certainty for each target vehicle can be displayed on a display screen.

Abstract: A flight control system and method for controlling a circle-to-land (“CTL”) maneuver utilizes an airborne area navigator. The area navigator receives inputs on aircraft category, aircraft position and speed, airport navigation data and pilot supplied data. In response to this data, the area navigator calculates the necessary conditions for executing the CTL maneuver and outputs control commands to a flight director. The pilot then executes the CTL maneuver either manually using the information provided by the area navigator or by using the aircraft autopilot under the direction of the flight director.

Abstract: A process for automatic monitoring of aircraft during take-off or landing. By means of one or more monitoring instruments installed in the vicinity of an airport shots are taken of the aircraft during take-off or landing. These recorded images are stored in a data memory. Means are present which enable the monitoring instrument to detect the aircraft and to follow the movement of the aircraft. The recorded images are stored in the data memory for later evaluation.

Abstract: An aviation facility nominating device for an aircraft includes a position receiving component that receives position data indicating a position of the aircraft, an aviation data receiving component that receives aviation data associated with a plurality of aviation facilities, a facility selecting component for selecting aviation data for a selected plurality of the aviation facilities based on a position of the aircraft and a nominating component that nominates at least one but not all of the selected plurality of aviation facilities as a nominated aviation facility likely to be of interest to a pilot based on the position of the aircraft.

Abstract: A system, method, and computer program product for alerting an aircraft flight crew of an inconsistency during an instrument landing system (ILS) approach to a selected runway. The system includes a component configured to receive glideslope and localizer signals, and a component configured to determine aircraft approach angle to runway end. Also, a component configured to alert the aircraft flight crew of an approach inconsistency, if the determined aircraft approach angle to runway end is less than a threshold angular value and one or more parameters based on aircraft position and the received glideslope and localizer signals are met. The component configured to determine aircraft approach angle to runway end determines the aircraft approach angle to runway end based on aircraft geometric altitude, a vertical figure of merit, a horizontal figure of merit, runway elevation, and aircraft distance to runway threshold.

Abstract: An aircraft including an approach and landing system, including a navigation unit for providing navigation information, a weather radar unit for providing radar information, a processor which receives navigation information from the navigation unit and information from the weather radar unit, the processor unit providing an output representing information concerning the aircraft in accordance with the provided navigation information and radar information, a memory for storing information representing a scene, the processor unit correlating the stored scene information with the output representing information concerning the aircraft to provide a mapped scene, a display unit for displaying the output of said processor and the mapped scene, and a steppable frequency oscillator for providing a signal which is stepped in frequency to the weather radar unit, thereby providing an increased range resolution.

Abstract: An airport surface movement guidance and control system (SMGCS) involving detection, integrated processing and graphical display of the relevant, in particular the safety-relevant, positions and movements of aircraft, and optionally, vehicles, on airside (runway, taxiways, apron) and in the relevant airport airspace. At least one radar detects the positions and movements between airborne and parked positions of the aircraft. The relevant data are displayed after data concentration on the monitor of at least one controller station in graphical form and/or letter or number form. As a result, the operational management of the surface movement can be planned and executed from the at least one controller station by means of solely the SMGC system.

Abstract: Disclosed are a global navigation satellite system (GNSS) landing system (GLS) and methods of using the same to calculate a vertical deviation from the glide slope of the aircraft. A GNSS antenna and position determining circuitry are used to determine the position of the aircraft as a function of received GNSS positioning signals. Vertical deviation computation circuitry coupled to the position determining circuitry calculates an angular vertical deviation &agr;v from the glide slope of the aircraft as a function of the total horizontal distance between the aircraft and a GLS elevation reference point (GERP).

Abstract: A window-passage detection system has a ground system comprising: a first course generator (3) for generating a horizontal DDM (Differential Depth of Modulation) pattern for defining a horizontal width (25) of a virtual window frame by emitting a first carrier signal and a first side-band signal from a pair of first transmission antennae (6a and 6b), a second course generator (4) for generating a vertical DDM pattern for defining a vertical width (26) of the virtual window frame by emitting a second carrier signal and a second side-band signal from a pair of second transmission antennae (7a and 7b), and a third course generator (5) for generating a longitudinal DDM pattern for defining a longitudinal position (27) of the virtual window frame by emitting a third carrier signal and a third side-band signal from a pair of third transmission antenna (8a and 8b). Pairs of the first to the third transmission antennae (6a to 8b) generate three orthogonal polarization planes.

Abstract: A programmable digital radio is configured to perform navigation functions. A receiver in the programmable digital radio receives analog signals from a navigation unit and digitizes the analog signals to produce digital navigation signals. The digital navigation signals are processed digitally and valid navigation information is determined. Processing includes generation of baseband signals including in-phase signals and quadrature signals, AM demodulation, filtering, decimating, demultiplexing, discrete fourier transformation, and function processing according to a selected function. The selected functions may include Localizer, Marker Beacon and Glideslope.